Delivery rotary-wing aircraft

ABSTRACT

A delivery rotary-wing aircraft has a plurality of rotary wings, a central portion to which a plurality of arms for supporting the rotary wings are connected, a first mounting portion for loading a package, a second mounting portion which is located on the opposite side to the first mounting portion as viewed from the central portion, a first supporting member for coupling the first mounting portion with the central portion, and a connection portion between the central portion and the first supporting member. The center point of lift occurring in the rotary-wing aircraft with the rotation of the plurality of rotary wings and the center point of gravity of the rotary-wing aircraft coincide with the center point of the connection portion. The first supporting member is equipped with an adjustment mechanism for vertically downwardly extending the length of the first supporting member.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a division of U.S. patent application Ser. No.16/338,970, filed Apr. 2, 2019, which is a U.S. National Stage ofPCT/JP2016/079369, filed Oct. 3, 2016.

TECHNICAL FIELD

The present invention relates to a delivery rotary-wing aircraft, andmore specifically, to a delivery rotary-wing aircraft capable of stablylanding on a destination without being affected by an updraft occurringin high-rise buildings or the like.

BACKGROUND ART

A rotary-wing aircraft called a drone or multicopter is used in variousfields such as security, agriculture, infrastructure monitoring and thelike. By utilizing the rotary-wing aircraft, it is also possible toobserve a phenomenon occurring at places where human beings cannotapproach such as disaster sites and undeveloped regions, and to analyzethe observed big data. Among the rotary-wing aircrafts, particularly, asmall-sized and light-weight rotary-wing aircraft is suitably usedmainly as a rotary-wing aircraft for aerial photography.

By using such a rotary-wing aircraft, it is possible to make “panoramicaerial photography” in which high-rise building construction sites suchas a Lower apartment can be photographed at high resolution.

In recent years, small-sized and light-weight rotary-wing aircrafts havebeen studied as tools for delivering packages such as package deliveryservice. Patent Document 1 discloses a delivery system using arotary-wing aircraft. (for example, Patent Document 1). Theaforementioned delivery system forms inventory of items for deliveringto a package delivery destination by an automated rotary-wing aircraft(drone). Further, the patent applicant hereby presents the followingpatent document as the invention described in a publication relating tothe present invention.

CITATION LIST Patent Document

-   Patent Document. 1: US Patent Application Publication No.    2015-0120094 A1

SUMMARY OF THE INVENTION Technical Problem

However, the rotary-wing aircraft used in the delivery system describedin Patent Document 1 is not configured as a rotary-wing aircraft capableof coping with an updraft occurring in high-rise buildings or the like.Rotary-wing aircraft, which is now referred to as a delivery rotary-wingaircraft, is a rotary-wing aircraft in which a general rotary-wingaircraft used for the rotary-wing aircraft for aerial photography isdiverted as it is as a delivery rotary-wing aircraft. When a generalrotary wing aircraft is diverted to a delivery rotary-wing aircraft, thefollowing technical problems occur.

Typical rotary-wing aircrafts are inclined obliquely by wind. In thecase of diverting a typical rotary-wing aircraft to a deliveryrotary-wing aircraft, it is required to maintain the position of thepackage before and during the delivery as it is and to quickly deliverthe package from a departure place to a destination. This is because, asthe rotary-wing aircraft is inclined, the package delivered by therotary-wing aircraft is also inevitably inclined.

Typical rotary-wing aircrafts tend to be easily inclined by wind. Inaddition, it is necessary to be inclined to travel forward. In the eventthat the package delivered by the rotary-wing aircraft is inclined atany moment, the commodity value of the package is lost. In particular,when the package delivered by the rotary-wing aircraft is a foodcontaining home delivery pizza, home-delivery sushi, westernconfectionery and a liquid such as beverages, the business loss due tothe inclination of the rotary-wing aircraft is significant. The sameapplies even if the rotary-wing aircraft is used to deliver dailynecessities.

Further, at a timing just before a general rotary-wing aircraft lands onthe destination, the rotary-wing aircraft may be inclined by an airflowoccurring in high-rise buildings or the like. A typical rotary-wingaircraft inclined by an airflow first allows a leg on one side of therotary-wing aircraft to make contact with the destination. After that,the rotary-wing aircraft has to contact a leg on the other side to thedestination. It is not possible to maintain the inclination of theaircraft body properly counteracting the airflow after the leg on oneside of the rotary-wing aircraft makes contact with the destinationuntil the leg on the other side makes contact with the destination. As aresult, there may be a case where the aircraft body flows along theblowing wind or the balance is lost and it is overturned. That is, dueto the airflow occurring at the destination, the rotary-wing aircrafthas a problem that it is turned over just before landing at thedestination. In particular, when the gain is set to be high in order tocope with a payload loaded on a lower part by a general rotary-wingaircraft, the possibility of overturning is high.

In addition, the package delivered by a rotary-wing aircraft must bedelivered from a delivery destination to a target destination within afew minutes to several tens of minutes depending on the goods accordingto the customer's request. If the goods are not delivered quickly, thecommodity value will be lost.

However, the flying speed of a typical rotary-wing aircraft is notsufficient in terms of delivering goods quickly.

The rotary-wing aircraft has to deliver a package accurately from adelivery location to a target destination. The operator of therotary-wing aircraft accurately needs to grasp the current position bymeans of a GPS device or the like on the way from the delivery locationto the destination, and then to steer the rotary-wing aircraft. However,when the rotary-wing aircraft is inclined, the GPS antenna provided inthe rotary-wing aircraft is also inclined. As a result, there is aproblem that the GPS receiving sensitivity of the rotary-wing aircraftis lowered. Furthermore, there is a problem that immediately afterdelivery of a package from the rotary-wing aircraft, the aircraft losesits balance and overturns or falls.

It is therefore an object of the present invention to provide a deliveryrotary-wing aircraft capable of solving various technical problems whichmay occur when a general rotary-wing aircraft is diverted for delivery,capable of stably landing on a destination, particularly without beingaffected by an updraft, and capable of stably continuing the flight evenafter delivering the package.

Technical Solution

The present inventors have conducted intensive studies, and have foundthat by controlling the center of gravity of the rotary-wing aircraftdownward against an updraft, it is possible to stably land on adestination without being affected by the updraft, and further thebalance is not lost even after separating the package from therotary-wing aircraft, thereby completing the present invention.Specifically, the present invention comprises the following technicalsubject matters.

(1) A delivery rotary-wing aircraft including:

a plurality of rotary wings,

a central portion to which a plurality of arm portions for supportingthe rotary wings are connected,

a first mounting portion for loading a package,

a second mounting portion which is located on the opposite side to thefirst mounting portion as viewed from the central portion,

a first supporting member for connecting the first mounting portion withthe central portion, and

a connection portion between the central portion and the firstsupporting member,

characterized by being controlled in such a manner that

the center point of lift occurring in the rotary-wing aircraft with therotation of the plurality of rotary wings and the center point ofgravity of the rotary-wing aircraft coincide with the center point ofthe connection portion, and

the first supporting member is equipped with an adjustment mechanism forvertically downwardly extending the length of the first supportingmember.

(2) The delivery rotary-wing aircraft according to the item (1),characterized in that the first supporting member comprises an outercylindrical supporting member and an inner cylindrical supportingmember, the inner cylindrical supporting member is accommodated in theouter cylindrical supporting member, and the inner cylindricalsupporting member slides downward to thereby vertically downwardlyextend the length of the first supporting member.

(3) The delivery rotary-wing aircraft according to the items (1) or (2),characterized in that the second mounting portion has a control meanswhich measures the acceleration at the time of landing of therotary-wing aircraft or the numbers of rotations of the plurality ofrotary wings, and changes the numbers of revolutions of the plurality ofrotary wings against the vertically upward updraft applied to therotary-wing aircraft.

(4) The delivery rotary-wing aircraft according to any one of the items(1) to (3), characterized in that the first supporting member has ajoint portion between the connection portion and the first mountingportion.

(5) The delivery rotary-wing aircraft according to the item (4),characterized in that, when the rotary-wing aircraft moves in thehorizontal direction, the first supporting member is horizontallypositioned by bending the first supporting member in the travelingdirection with the joint portion as a fulcrum.

Advantageous Effects

According to the present invention, there is provided a deliveryrotary-wing aircraft capable of stably landing on a destination withoutbeing affected by an updraft. In addition, according to the presentinvention, in the case where the payload of the rotary-wing aircraft isincreased by the package loaded on the rotary-wing aircraft, there isprovided a delivery rotary-wing aircraft capable of stably flyingwithout losing its balance even after the package is separated from therotary-wing aircraft. Further, according to the present invention, thereis provided a delivery rotary-wing aircraft which improves the maximumspeed at the time of flight and thus improves fuel economy.

BRIEF DESCRIPTION OF DRAWINGS

FIG. 1 is a perspective view showing a configuration of a deliveryrotary-wing aircraft according to one embodiment of the presentinvention.

FIG. 2 is a side view of a delivery rotary-wing aircraft.

FIG. 3 is a model diagram showing a mode in which an arm portion of thedelivery rotary-wing aircraft is inclined.

FIG. 4 is a view showing the center point of gravity of the deliveryrotary-wing aircraft.

FIG. 5 is a diagram showing a flight mode when the delivery rotary-wingaircraft takes off a departure place and completes the horizontalmovement posture.

FIG. 6 is a diagram showing a flight mode when the delivery rotary-wingaircraft horizontally moves, arrives above the destination, and thenenters the landing posture.

FIG. 7 is a view showing a state (a) before the first supporting memberof the delivery rotary-wing aircraft is extended and a state (b) afterthe first supporting member is extended.

FIG. 8 is a diagram showing when the delivery rotary-wing aircraft landson the destination and completes the delivery of the package.

FIG. 9 is a diagram showing a flight mode when a delivery rotary-wingaircraft from which the package is separated moves from a destination toa departure place.

DETAILED DESCRIPTION OF EMBODIMENTS First Embodiment

<Delivery Rotary-Wing Aircraft>

FIG. 1 is a perspective view showing an outline of a deliveryrotary-wing aircraft of the present invention. As shown in FIG. 1 , thedelivery rotary-wing aircraft 1 includes: a plurality of rotary wings12, a central portion 20 to which a plurality of arm portions 16 forsupporting the rotary wings 12 are connected, and a plurality of rotarywing portions 10 provided at the outer circumferential direction and atthe end portions of the plurality of arm portions 16. A control deviceor the like is mounted on the central portion 20. Further, the deliveryrotary-wing aircraft 1 includes a first mounting portion 30 for loadinga package L on the lower portion of the central portion 20, and a secondmounting portion 40 for loading a battery, a GPS antenna, and the likeon the upper portion of the central portion 20.

The delivery rotary-wing aircraft 1 shown in FIG. 1 has four armportions, but the number of the arm portions is not limited thereto. Forexample, the arm portions of the delivery rotary-wing aircraft 1 may beprovided with six, eight, twelve or the like arm portions. In the casewhere the delivery rotary-wing aircraft 1 of the present inventionstably flies and delivers a heavy package, the number of the armportions is preferably six or more. In the first embodiment, a deliveryrotary-wing aircraft 1 having four arm portions, which is the simplestrotary-wing aircraft, will be described.

The central portion 20 of the delivery rotary-wing aircraft 1 is locatedat the center in a circular ring formed by connecting the tip portionsof the arm portions 16 when the delivery rotary-wing aircraft 1 isviewed from the right overhead. In the central portion 20, a planarshape constituted by a flat plate has a disk shape. Four arm portions16A to 16D are extended toward the outer circumference of a circularring formed by connecting the tip portion of the arm portion 16 from theside surface of the central portion 20. The four arm portions 16A to 16Dare provided in four directions so as to be equally spaced in thecircular ring. The four arm portions 16A to 16D are provided so that theinterval between adjacent arm portions becomes 90°. In addition, the armportion 16 may have a linear shape, or may have a bent shape based on alinear shape from a design standpoint.

The arm portions 16A to 16D are members supporting the correspondingrotary wing portions 10A to 10D, respectively. In order to stabilize thearm portions 16A to 16D, the outer periphery of a circular ring formedby connecting from the side face of the central portion 20 to the endportion of the arm portion 16 may be connected by using a propellerguard (not shown) such as a circular shaped member or the like. Acoloring body such as an LED may be installed on the side surface of thecircular shape in order to indicate the flying state of the rotary-wingaircraft.

Since the arm portions 16A to 16D have the same structure, the structureof the arm portion 16A will be mainly described. A rotary wing portion10A is provided at the tip portion of the arm portion 16A which is inthe outer peripheral direction as viewed from a central portion 20. Therotary wing portion 10A includes a rotary wing 12A and a power section14A. The rotary wing 12A rotates in response to the output from thepower section 14A. By rotating the rotor wing 12A, the deliveryrotary-wing aircraft 1 generates a propelling force to take off adeparture place, to move horizontally, and to land on the destination.Further, the rotary wing 12A can rotate rightward, stop, and rotateleftward.

The power section 14A is a drive device for rotating the rotary wing12A. The power section 14A is not particularly limited as long as it isa means which can drive the rotary wing 12A. For example, an internalcombustion engine, an electric motor, or the like may be used. The powersections 14A to 14D correspond to the rotary wings 12A to 12D,respectively.

As shown in FIG. 1 , the rotary wing 12A is diagonally opposed to therotary wing 12C and rotates in the same rotation direction. The rotarywing 12B is diagonally opposed to the rotary wing 12D and rotates in thesame rotation direction. The rotational direction of the rotary wing 12Ais different from that of the rotary wing 12B. For example, the powersection 14A that drives the rotary wing 12A may be an electric motor forright rotation, and the power section 14B that drives the rotary wing12B may be an electric motor for left rotation.

The delivery rotary-wing aircraft 1 has a first mounting portion 30. Thefirst mounting portion 30 is located at a lower position as viewed fromthe central portion 20. The first mounting portion 30 can load a packageL. The first mounting portion 30 always maintain its shape verticallydownward so that the position of the loaded package L and the state ofthe package L can be maintained. The first mounting portion 30 is notparticularly limited as long as it can store the package L. The packageL loaded in the first mounting portion 30 is an undesirable package ifit is inclined or if the loaded position is changed. Therefore, thefirst mounting portion 30 must always maintain a stable position.

Further, the first mounting portion 30 may have a support motor (notshown). The state of the package L loaded on the first mounting portion30 can be more stably maintained by providing the support motor.

The first mounting portion 30 may include a removable storage box 30 aand a mounting portion 30 b for mounting the storage box 30 a. In casewhere the storage box 30 a can be transferred at the delivery place,after the delivery of the package L is completed, the storage box 30 amay be removed from the mounting portion 30 b of the first mountingportion 30, so that the first mounting portion 30 may be only themounting portion 30 b. Further, in place of the storage box 30 a, asimple package holding means (not shown) such as a net may be employed.

The storage box 30 a may employ a structure capable of heat retention orheat insulation in order to maintain the temperature inside the box. Thestorage box 30 a may have a lid for the storage box on the side of thebox. For example, the lid for the storage box may be a lid of a typethat can be slidably fitted into a groove (not shown) provided in thestorage box 30 a.

The delivery rotary-wing aircraft 1 has a second mounting portion 40.The second mounting portion 40 is located on the upper side which is theopposite side as viewed from the central portion 20. The second mountingportion 40 mainly includes members and devices necessary for driving andcontrolling the delivery rotary-wing aircraft 1. Examples of necessarymembers and devices include a drive battery, a receiver for receiving asignal from a transmitter operated by an operator, a control device, aninfrared sensor, a GPS antenna for receiving positioning signals, andthe like.

The control device includes a sensor for measuring the position anddirection of the rotary-wing aircraft, a sensor for measuring the speedand acceleration of the rotary-wing aircraft, a measuring device formeasuring the rotational direction and the number of rotations of therotary wing, a measuring device for measuring the weight of therotary-wing aircraft, a load (payload) at the time of loading a package,a central processing unit (CPU), and the like.

The delivery rotary-wing aircraft 1 is provided with a first mountingportion 30 on the lower side and a second mounting portion 40 on theupper side, around the central portion 20. The central portion 20 andthe first mounting portion 30 are connected via a first supportingmember 24. The central portion 20 and the second mounting portion 40 areconnected via a second supporting member 26. A connecting portion 22 isprovided just below the central portion 20 so as to come into contactwith the lower surface of the central portion 20. The connecting portion22 is provided between the lower surface of the central portion 20 andthe first supporting member 24.

For example, the connecting portion 22 may be a hollow member having abiaxial gimbal structure. Further, the connecting portion 22 may be amember such as a ball joint that comprises a ball stud with a round barattached to a metal ball and a socket 22 a in spherical contact with theball stud. Since the connecting portion 22 has a biaxial gimbalstructure, it swings in an arbitrary direction. The connecting portion22 swings in an arbitrary direction along the spherical surface. As theconnecting portion 22 swings in an arbitrary direction, the centralportion 20 is arbitrarily swung. The plane formed by the arm portions16A to 16D attached to the central portion 20 is inclined at a constantangle.

FIG. 2 is a side view of a delivery rotary-wing aircraft 1. FIG. 2 is aside view of the delivery rotary-wing aircraft 1 shown in FIG. 1 asviewed from the X direction. FIG. 3 is a model diagram showing a shapein which an arm portion 16 of the delivery rotary-wing aircraft 1 shownin FIG. 2 is inclined.

FIG. 3 is a model diagram showing a mode in which the plane formed bythe arm portions 16A to 16D is inclined. In the delivery rotary-wingaircraft 1, the connecting portion 22 can make the plane formed by thearm portions 16A to 16D inclined. In the delivery rotary-wing aircraft 1shown in FIG. 3 , the arm portion 16A can be positioned downward and thearm portion 16B can be positioned upward by making the connectionportion 22 inclined leftward. Further, when the connecting portion 22 ofthe delivery rotary-wing aircraft 1 is inclined leftward, the numbers ofrotations of the rotary wings 12A and 12D may be set to be smaller thanthe numbers of rotations of the rotary wings 12B and 12C.

The delivery rotary-wing aircraft 1 is controlled such that the centerpoint Cf of lift occurring by the rotation of the plurality of rotarywings and the center point Cg of gravity of the rotary-wing aircraftcoincides with the center point C of the connection portion 22. Theconnection portion 22 has a center point C. The center point C of theconnection portion 22 is the center point Cg of the gravity of thedelivery rotary-wing aircraft 1 when the package is loaded. FIG. 4 is amodel diagram showing the center point Cg of gravity of the deliveryrotary-wing aircraft 1.

As shown in FIG. 4 , the center point Cg is set on a supporting memberformed by the first supporting member 24 and the second supportingmember 26. In FIG. 4 , the center point Cg is determined inconsideration of the balance of the weight generated by a first mountingportion 30 present on the right side, a package L loaded on the firstmounting portion 30, a first supporting member 24 and the like, and theweight generated by a second mounting portion 40 present on the leftside, a member mounted on the second mounting portion 40, a secondsupport member 26 and the like. Further, FIG. 4 is a model diagramshowing the balance of a seesaw.

In consideration of the balance of the weight, the support point on thesupporting member composed of the first supporting member 24 and thesecond supporting member 26 becomes the center point Cg. The centerpoint Cg measures the weight on the right and left sides by a weightsensor mounted on the second mounting portion 40, and determines asupport point by a central processing unit (CPU) mounted on the secondmounting section 40, and the support point is defined as the centerpoint Cg.

At the same time, the center point C of the connecting portion 22 isalso the center point Cf of the lift generated in the deliveryrotary-wing aircraft 1 by the rotation of the rotary wings 12A to 12D.The center point Cf is determined by a central processing unit (CPU)mounted on the second mounting portion 40 by measuring the number ofrevolutions of the rotary wings, the rotating direction and the like bymeans of a rotary wing measuring sensor mounted on the second mountingsection 40.

The delivery rotary-wing aircraft 1 controls the center point C of theconnection portion 22 such that the center point Cg of gravity and thecenter point Cf of lift coincide with each other. That is, the deliveryrotary-wing aircraft 1 makes the center point Cg of gravity and thecenter point Cf of lift coincide with the center point C. Therefore, arotation motion due to gravity caused by the first supporting member 24,the first mounting portion 30, the package L loaded on the firstmounting portion 30 or the like does not occur around the center pointCf of the lift. The delivery rotary-wing aircraft 1 focuses on thegravity and lift applied to the rotary-wing aircraft and suppresses therotation moment caused by the gravity so that the numbers of rotationsof the rotary wings 12A to 12D can be maintained at the same number ofrevolutions.

As a first technical feature, the delivery rotary-wing aircraft 1 cancounteract the vertically upward updraft that is applied to therotary-wing aircraft. That is, even if the delivery rotary-wing aircraft1 receives an updraft by high-rise buildings or the like after arrivingabove the destination, it can stably land on the destination withoutmaking the rotary-wing aircraft itself unstable.

After arriving above the destination, the delivery rotary-wing aircraft1 allows the center of gravity of the rotary-wing aircraft to movedownward so as to counteract the updraft caused by a high-rise buildingor the like. It is possible to oppose to an updraft by moving the centerof gravity of the delivery rotary-wing aircraft 1 downward. In order tomove the center of gravity of the delivery rotary-wing aircraft 1downward, the length of the first supporting member 24 is changed so asto extend the first supporting member 24 in the downward direction. Thelength of the first supporting member 24 is extended by an adjustmentmechanism 242 provided in the delivery rotary-wing aircraft 1. Inaddition, the distance between the second supporting member 26 and thecentral portion 20 is set to be short by moving the second mountingportion 40 in the direction of the central portion 20.

The adjustment mechanism 242 is not particularly limited as long as ithas a structure capable of changing the length of the first supportingmember 24. For example, the adjustment mechanism 242 may have acylindrical structure having stretchability. The first supporting member24 is composed of a first supporting member 24 a and a first supportingmember 24 b. The first supporting member 24 a is an outer cylindricalpart and the first supporting member 24 b is an inner cylindrical partto accommodate the first supporting member 24 b in the first supportingmember 24 a. The first supporting member 24 b can slide downward withrespect to the first supporting member 24 a, and is fixed at apredetermined position inside the first supporting member 24 a.

As the adjustment mechanism 242, the following structure may be adopted.In order to slide the first supporting member 24 b downward with respectto the first supporting member 24 a, the first supporting member 24 bmay be pin-fixed by a pin passing through the inner wall from the outerside wall of the first supporting member 24 a toward the inner wall ofthe first supporting member 24 b.

When the first supporting member 24 b is slid downward to extend thefirst supporting member 24, the first supporting member 24 b pin-fixedin the first supporting member 24 a can be slid downward by pulling outthe pin. As a result, the length of the first supporting member 24 canbe extended. As a result, the center of gravity of the deliveryrotary-wing aircraft 1 can be moved downward. Further, the adjustmentmeans 242 comprises two supporting members composed of an outer cylinderand an inner cylinder, but may be further provided with an innercylinder inside the inner cylinder so as to be composed of three or moresupporting members.

The length of the first supporting member 24 after extension can beappropriately set. The length of the first supporting member 24 afterextension is determined in consideration of the weight of therotary-wing aircraft 1, the package (payload) loaded on the firstmounting portion 30, and the like. For example, when a rotary-wingaircraft that is loading a predetermined package (payload) is subjectedto an updraft, the length of the first supporting member 24 afterextension which is necessary for performing the movement of the centerof gravity in the downward direction is set.

The first supporting member 24 is appropriately selected inconsideration of the weight of the delivery rotary-wing aircraft 1, thepackage (payload) loaded on the first mounting portion 30, and the like.It is possible to set the length of the extended first supporting member24 and its structure which are required when the delivery rotary-wingaircraft 1 receives the updraft.

In addition, as the adjustment mechanism 242, for example, arack-and-pinion, a steering gear mechanism used for focusing in anoptical apparatus or the like may be adopted.

The delivery rotary-wing aircraft 1 may change the number of rotationsof the rotary wing in addition to moving the center of gravity of therotary-wing aircraft downward. Here, “changing the number of rotations”includes decreasing the number of rotations of the rotary wings rotatingin a certain direction, stopping the rotation of the rotary wing, andreversing the direction of rotation. By changing the number ofrevolutions of the rotary wings in this way, the gravity of the deliveryrotary-wing aircraft 1 can be generated to oppose to the updraft.

As a second technical feature, the delivery rotary-wing aircraft 1 doesnot lose its balance even after the package is separated from therotary-wing aircraft. As a result, the delivery rotary-wing aircraft 1does not overturn or fall. This is because the delivery rotary-wingaircraft 1 has already moved the center of gravity of the rotary-wingaircraft downward before separating the package from the rotary-wingaircraft.

When a typical rotary-wing aircraft is loaded with the package, thecenter of gravity of the rotary-wing aircraft is moved greatly upward byseparating the package from the rotary-wing aircraft. As a result, thetypical rotary-wing aircraft greatly breaks its balance, which willoverturn and fall.

However, in the delivery rotary-wing aircraft 1 of the presentinvention, even when the center of gravity of the rotary-wing aircraftis moved upward by separating the package from the rotary-wing aircraft1, the length of the first supporting member 24 is already extendeddownward, and thus, the center of gravity of the rotary-wing aircraftdoes not move. In the delivery rotary-wing aircraft 1, the movement ofthe center of gravity in the upward direction caused by the separationof the package from the rotary-wing aircraft 1 is canceled by themovement of the center of gravity in the downward direction.

That is, by extending the first supporting member 24 in the downwarddirection, the rotary-wing aircraft 1 of the present invention can notonly move its center of gravity downward against the updraft, but alsothe movement of the center of gravity upward can be canceled immediatelyafter the package is separated from the rotary-wing aircraft.

The first supporting member 24 of the delivery rotary-wing aircraft 1includes a joint portion 28 which is provided on the first supportingmember 24 and positioned between the upper portion of the mountingportion 30 b of the first mounting portion 30 and the lower portion ofthe first supporting member 24. The joint portion 28 can be rotated sothat the first supporting member 24 is bent in the traveling directionof the delivery rotary-wing aircraft 1, with the joint portion 28 as afulcrum. The angle at which the joint portion 28 is bent is notparticularly limited. It can be set appropriately according to theconditions under which the delivery rotary-wing aircraft 1 is flying.For example, even if the first supporting member 24 is bent at 90° inthe traveling direction, the first mounting portion 30 is alwayssuspended vertically downward. The package L loaded on the firstmounting portion 30 is delivered up to the destination while maintainingthe position and condition at the departure place.

The joint portion 28 is driven by a signal from a control device mountedon the central portion 20. The joint portion 28 receives a signal fromthe control device and bends the first supporting member 24 with thejoint portion 28 as a fulcrum by a drive motor (not shown) provided inthe joint portion 28. In addition, the joint portion 28 has a lockmechanism. The first supporting member 24 holds the angle (for example,90°) appropriately set according to the conditions under which thedelivery rotary-wing aircraft 1 is flying, and is fixed by the lockmechanism at the bent position.

Further, the joint portion 28 is fixed, for example, by a lock mechanismat a position where the first supporting member 24 is bent at 90° in thetraveling direction, rotates at 90° in the direction opposite to thetraveling direction, so that it can return to the initial state. Whenthe joint portion 28 returns to the initial state, the first supportingmember 24 becomes a vertically upward direction, and the firstsupporting member 24 and the second supporting member 26 are arranged ina straight line.

<Flight Mode of Delivery Rotary-Wing Aircraft>

Hereinafter, the flight mode of the delivery rotary-wing aircraft 1 ofthe present invention will be described. In the following description,the flight mode of the delivery rotary-wing aircraft 1 is explained bydividing it into two routes: route A “from a departure place to adestination” and route B “from a destination to a departure place”.

(Route A “from a Departure Place to a Destination”)

Route A is a flight route when the delivery rotary-wing aircraft 1loaded with a package L takes off a departure place and lands on thedestination, and the package L is unloaded from the delivery rotary-wingaircraft 1 loaded with the package L at the destination, to therebycomplete the delivery (package delivery service) of the package L. Theflight route and posture of the delivery rotary-wing aircraft 1 aremeasured all the time by a GPS antenna and an infrared sensor providedin the second mounting section 40.

FIG. 5 is a diagram showing a flight mode when the delivery rotary-wingaircraft 1 takes off from a departure place, stops in the air (hovering)and completes the horizontal movement posture. At the departure place,the package L to be delivered to a destination is loaded on the firstmounting portion 30 of the delivery rotary-wing aircraft 1. The packageL is stored in the storage box 30 a which is the first mounting portion30. The package L is fixed so as not to move within the storage box 30a. After the package L is stored in the storage box 30 a which is thefirst mounting portion 30, the lid closing may be performed by a lidfrom the side surface of the storage box 30 a so that the package L doesnot come into contact with an external air.

The operator operates a radio control transmitter having the operatingunit and raises the output of the power sections 14A to 14D of therotary wing portions 10A to 10D to increase the numbers of rotations ofthe rotary wings 12A to 12D. Due to the rotation of the rotary wings 12Ato 12D, the lift necessary to float the delivery rotary-wing aircraft 1occurs vertically upward. When the lift exceeds the gravity acting onthe delivery rotary-wing aircraft 1, the delivery rotary-wing aircraft 1leaves the ground and takes off a departure place.

(A) Aerial Stopping (Hovering)

The delivery rotary-wing aircraft 1 ascends by increasing the rotationspeed of the rotary wings 12A to 12D. Thereafter, the deliveryrotary-wing aircraft 1 continues to ascend and reaches a certainaltitude. The delivery rotary-wing aircraft 1 that reaches a certainaltitude performs an aerial stopping (hovering) at the altitude. Thealtitude is appropriately determined by the flight route of the deliveryrotary-wing aircraft 1, the height of buildings such as high-risebuildings, the aerial law applied to the delivery rotary-wing aircraft1, and the like. The operator may preset the altitude at which thedelivery rotary-wing aircraft 1 performs an aerial stopping (hovering)in consideration of various conditions.

Since the weight applied to the delivery rotary-wing aircraft 1, and thelift generated in the delivery rotary-wing aircraft 1 by the rotation ofthe rotary wings 12A to 12D are dynamically balanced, the rotary-wingaircraft can be stopped in the air (hovering). The numbers of rotationsof the rotary wings 12A to 12D are maintained at a constant level.Aerial stopping (hovering) is performed in order for the deliveryrotary-wing aircraft 1 to start preparation for horizontal movementposture. Further, in FIG. 5 , it is assumed that when the deliveryrotary-wing aircraft 1 is subjected to rotation-aerial stopping(hovering), the numbers of revolutions of the rotary wings 12A to 12Dare level (6) among 10 stages (levels (1) to (10)).

(B) Inclination of Arm Portion

The arm portion 16 of the delivery rotary-wing aircraft 1 which issubjected to aerial stopping (hovering) is kept horizontal and is notinclined with respect to the horizontal direction. Thereafter, the armportion 16 is inclined forwardly downward so that the rotary wings 12Aand 12D, which are front rotary wings, are lower than the rotary wings12B and 12C which are rear rotary wings with respect to the travelingdirection of the delivery rotary-wing aircraft 1. When the arm portion16 inclines forwardly and downwardly, the numbers of rotations of thefront rotary wings 12A and 12D are made smaller than the numbers ofrotations of the rear rotary wings 12B and 12C, and the numbers ofrotations of the rear rotary wings 12B and 12C are increased. Further,in FIG. 5 , when the delivery rotary-wing aircraft 1 inclines the armportion 16, the numbers of revolutions of the rotary wings 12A and 12Don the front side are set to level (4), and the numbers of rotations ofthe rotary wings 12B and 12C on the rear side is set to level (6).

(C) Adjustment of the Numbers of Rotations of Rotary-Wings

Next, the delivery rotary-wing aircraft 1 adjusts the numbers ofrotations of the rotary wings 12A to 12D after inclining the arm portion16 while hovering (aerial stopping). Even in the case where the armportion 16 is inclined, the delivery rotary-wing aircraft 1 can make thenumbers of rotations of all the rotary wings 12A to 12D equal.

This is because the delivery rotary-wing aircraft 1 of the presentinvention is designed so that the point of action of gravity of therotary-wing aircraft 1 is a connecting portion 22, and the connectingportion 22 is the center point of the lift of the delivery rotary-wingaircraft 1. That is, the center point of gravity of the deliveryrotary-wing aircraft 1 physically completely coincides with the centerpoint of the connecting section 22, which is a center point of lift ofthe delivery rotary-wing aircraft 1. Further, in FIG. 5 , after thedelivery rotary-wing aircraft 1 adjusts the numbers of rotations of therotary wings, the numbers of rotations of the rotary wings 12A to 12Dare set to level (5).

(D) Transition to Horizontal Movement Posture

Next, the delivery rotary-wing aircraft 1 rotates the second supportingmember 26 and the first supporting member 24 to the left at 90° so thatthe second mounting part 40 is the most distal part with the joint part28 as a fulcrum. The joint portion 28 is stopped at a position where thesecond mounting portion 40 is rotated to the left, for example, at 90°,and is fixed by a lock mechanism or the like at the position. Thedelivery rotary-wing aircraft 1 always keep the direction of the firstmounting portion 30 vertically downward only by rotating the jointportion 28 as a fulcrum. Therefore, the package L loaded on the firstmounting portion 30 is not inclined.

The form of the delivery rotary-wing aircraft 1 is a horizontal movementposture. Then, the delivery rotary-wing aircraft 1 horizontally movesthe distance from the air above the departure place to the air over thedestination while maintaining the horizontal movement posture. Thehorizontal movement posture is the flight mode adopted for the longesttime while the delivery rotary-wing aircraft 1 is flying.

(E) Horizontal Movement Posture

In the delivery rotary-wing aircraft 1, by making the arm portion 16inclined, the forward inclined posture is maintained in a state of beinginclined downwardly with respect to the traveling direction, and thenumbers of rotations of the rotary wings 12A to 12D on which the armportion 16 is mounted can be equalized. The delivery rotary-wingaircraft 1 does not need to set the numbers of revolutions of the rotarywings 12B, 12C on the rear side in the traveling direction larger thanthe numbers of revolutions of the rotary wings 12A, 12D on the frontside.

Since the arm portion 16 maintains the forward inclined posture in astate where the arm portion 16 descends frontward with respect to thetraveling direction, it is possible to remarkably reduce an airresistance until the delivery rotary-wing aircraft 1 moves horizontallyand reaches up to the air over the destination.

The delivery rotary-wing aircraft 1 of the present invention can makethe numbers of rotations of the rotary wings 12A to 12D equal. That is,in the delivery rotary-wing aircraft 1, it is unnecessary to increasethe numbers of rotations of the rear rotary wings 12B, 12C in thetraveling direction to be greater than the numbers of rotations of thefront rotary wings 12A, 12D.

Therefore, there is no need to raise the output of the power sections14B, 14C of the rear rotary wings 12B, 12C. As a result, when the powersections 14A to 14D of the rotary wings 12A to 12D provided in thedelivery rotary-wing aircraft 1 are motors, the motor load can bedispersed. For this reason, the possibility that a power section of aspecific rotary wing will fail due to heat generation or the like isreduced. Further, in the delivery rotary-wing aircraft 1 can improvefuel economy by dispersing the motor load. By dispersing the motor load,a motor having low motor efficiency does not exist. In this way, thedelivery rotary-wing aircraft 1 can reduce the burden on the battery, sothat the reliability of the battery can be improved.

Further, when the delivery rotary-wing aircraft 1 moves horizontally,the second mounting portion 40 is the most distal end portion withrespect to the traveling direction. The horizontal movement posture ofthe delivery rotary-wing aircraft 1 can be almost linear. It is possibleto greatly reduce the air resistance when the delivery rotary-wingaircraft 1 moves horizontally.

That is, in the delivery rotary-wing aircraft 1, the first supportingmember 24 and the second supporting member 26 are arranged on a straightline, and by inclining the arm portion 16 on which the rotor wing 12 ismounted, and maintaining the forward inclined posture as the rotary-wingaircraft, the projection area with respect to the traveling directioncan be significantly reduced.

The flight posture of such delivery rotary-wing aircraft 1 contributesto improving the flight speed of the rotary-wing aircraft and improvingthe fuel economy of the rotary-wing aircraft.

In this way, the delivery rotary-wing aircraft 1 can improve the flightspeed of the horizontal movement speed, and can expand the range ofloadable package (payload). Furthermore, since the delivery rotary-wingaircraft 1 can make the numbers of rotations of the rotary wings 12A to12D equal, it is possible to improve fuel economy.

(F) Rotation of the Supporting Member

FIG. 6 is a model diagram until the delivery rotary-wing aircraft 1horizontally moves by adopting the horizontal movement posture, andarrives above the destination to complete the landing posture. In thedelivery rotary-wing aircraft 1, the second supporting member 26 and thefirst supporting member 24 are rotated rightward at 90° so that thesecond mounting portion 40 is directed vertically upward with a jointportion 28 as a fulcrum. The joint portion 28 stops at the positionwhere the second mounting portion 40 is rotated rightward at 90°, andthen is fixed at this position by a lock mechanism or the like. In thedelivery rotary-wing aircraft 1, the direction of the first mountingportion 30 is maintained vertically downward only by rotating the secondsupporting member 26 and the first supporting member 24 with the jointportion 28 as a fulcrum. Therefore, the package L loaded on the firstmounting portion 30 is not inclined.

Further, in FIG. 6 , the numbers of rotations of the rotary wings 12A to12D after rotation of the supporting member of the delivery rotary-wingaircraft 1 is set to level (5).

(G) Horizontal of Arm Portion

In the delivery rotary-wing aircraft 1 in which the second mountingsection 40 is vertically upward, the arm portion 16 is inclined forwardin the traveling direction. As the arm portion 16 increases the numbersof revolutions of the rotary wings 12A and 12D which are lower frontwardand decreases the number of revolutions of the rotary wings 12B and 12Cwhich are higher rearward, thereby holding the arm portion 16horizontally. As a result, the numbers of revolutions of the rotarywings are all equal. The delivery rotary-wing aircraft 1 takes a landingposture to a destination at an altitude H corresponding to the height ofa high-rise building.

Further, in FIG. 6 , when the arm portion 16 of the delivery rotary-wingaircraft 1 initiates a horizontal posture, the numbers of revolutions ofthe rotary wings 12A, 12D are set to level (6), and the rotation numbersof the rotary wings 12B and 12C are set to level (4).

FIG. 7 is a model diagram showing a state before extending the firstsupporting member 24 and a state after extending the first supportingmember 24, after the delivery rotary-wing aircraft 1 takes a landingposture to the destination. In FIG. 7(a), the first supporting member 24is provided with an adjustment means 242. A first supporting memberexisting between the adjustment means 242 and the joint portion 28 is244, and the length thereof is l1. As described above, the firstsupporting member 24 is composed of a first supporting member 24 b,which is an inner cylindrical part, with respect to the first supportingmember 24 a which is an outer cylindrical part. By operating theadjustment means 242, the first supporting member 24 b accommodated inthe first supporting member 24 a is protruded downward and fixed.

Further, when the adjustment means 242 has a screw structure, the screwmay be loosened. If the adjustment means 242 has a pin-fixing structure,the pin may be pulled out.

In FIG. 7(b), the first supporting member 24 has a first supportingmember 244 existing between the adjustment means 242 and the jointportion 28, and its length is l2. When the adjustment means 242 isoperated, the first supporting member 24 b is protruded downward andfixed. As a result, the length of the first supporting member 24 isextended the length of the first supporting member 24 b which is theinner cylinder.

FIG. 8 is a model diagram until the delivery rotary-wing aircraft 1receives an updraft by high-rise buildings or the like, lands on thedestination, unloads a package L, and completes the delivery of thepackage. The delivery rotary-wing aircraft 1 is affected by an updraftoccurring in a high-rise building or the like. The delivery rotary-wingaircraft 1 receives an updraft blown upward from the lower side towardthe upper side from the lower side of the rotary-wing aircraft. Theupdraft directly hits the bottom surface of the storage box 30 a of thefirst mounting portion 30 constituting the delivery rotary-wing aircraft1, and the rotary wing mounted on the arm portion 16. In FIG. 8 , thedestination may be a destination surface, or a courier heliportdedicated to the delivery rotary-wing aircraft 1 installed in ahigh-rise building.

When an upward force due to the updraft is applied to a generalrotary-wing aircraft, the rotary-wing aircraft loses its balance andfalls. However, the delivery rotary-wing aircraft 1 extends the firstsupporting member 24 vertically downward at the stage before an upwardforce due to an updraft is applied. The delivery rotary-wing aircraft 1lowers the center of gravity of the rotary-wing aircraft. By loweringthe center of gravity of the delivery rotary-wing aircraft 1, it ispossible to cancel the upward force applied to the delivery rotary-wingaircraft 1 by the updraft.

The delivery rotary-wing aircraft 1 lowers its center of gravity inorder to counteract the force generated by the updraft. The length ofthe first supporting member 24 required for lowering the center ofgravity is determined in relation to the force generated by the updraft.

In addition, the delivery rotary-wing aircraft 1 may lower the numbersof rotations of the rotary wings 12A to 12D in order to counteract theupdraft. By lowering the numbers of rotations of the rotary wings 12A to12D, gravity due to its own weight of the delivery rotary-wing aircraft1 is generated. Gravity due to its own weight of the deliveryrotary-wing aircraft 1 can counteract the force generated by theupdraft. Further, the delivery rotary-wing aircraft 1 may stop therotation of the rotary wings 12A to 12D in order to counteract the forcegenerated by the updraft. By stopping the rotation of the rotary wings12A to 12D, gravity due to its own weight is generated in the deliveryrotary-wing aircraft 1. Such a vertically downward force can counteractthe force generated by the updraft.

Further, the delivery rotary-wing aircraft 1 may move the position ofthe arm portion 16 downward to counteract the force generated by theupdraft. In order to move the position of the arm portion 16 in thedownward direction, the connecting portion 22 is moved downward.

As described above, by appropriately combining means for lowering thecenter of gravity of the delivery rotary-wing aircraft 1, the deliveryrotary-wing aircraft 1 of the present invention can counteract the forcegenerated by the updraft occurring in high-rise buildings or the like.

A general rotary-wing aircraft maintains the balance of the rotary-wingaircraft by adjusting a gain set in the rotary-wing aircraft. If thegain of the rotary-wing aircraft is set high, it is possible to stablymaintain the posture of the rotary-wing aircraft against the forceapplied to the rotary-wing aircraft. However, the rotary-wing aircraftis liable to cause hunting, resulting in a fall of the rotary-wingaircraft. On the other hand, if the gain of the rotary-wing aircraft isset low, the rotary-wing aircraft makes it difficult to generatehunting, but it is impossible to stably maintain the posture of therotary-wing aircraft against the force applied to the rotary-wingaircraft. As a result, the rotary-wing aircraft loses its balance andfall.

Since a general rotary-wing aircraft has to set a gain according to thetype of flight, the burden of the operator is great. However, in thedelivery rotary-wing aircraft 1 of the present invention, the center ofgravity is moved downward by extending the length of the firstsupporting member 21 supporting the first mounting portion 30 verticallydownward, and thus, it is possible to easily cope with the forcegenerated by the updraft. In other words, it is sufficient for thedelivery rotary-wing aircraft 1 to adjust its gain only once, andthereafter, there is no need to adjust the gain again.

(Separation and Detachment of Packages)

The delivery rotary-wing aircraft 1 lands on the destination and dropsoff the package L loaded on the first mounting section 30 to thedestination. The delivery rotary-wing aircraft 1 and the package L areseparated. Separation of the delivery rotary-wing aircraft 1 and thepackage L is performed by detaching a storage case 30 a loaded with thepackage L from the mounting portion 30 b of the first mounting portion30 and dropping off the baggage L to the destination.

Normally, immediately after the package L is separated from the deliveryrotary-wing aircraft 1, it is considered that the payload becomes small,and the center of gravity of the rotary-wing aircraft 1 moves upward.However, after arriving above the destination, the delivery rotary-wingaircraft 1 extends the first supporting member 24 vertically downward ata stage before receiving the updraft, and the delivery rotary-wingaircraft 1 lowers the center of gravity of the rotary-wing aircraftdownward. As the packages are separated from the delivery rotary-wingaircraft 1, movement of the center of gravity in the upward directiongenerated in the rotary-wing aircraft is canceled by the movement of thecenter of gravity in the downward direction of the rotary-wing aircraft.Thus, even after the packages are separated from the deliveryrotary-wing aircraft 1, the center of gravity of the rotary-wingaircraft does not move.

After the storage case 30 a is separated from the first mounting portion30, the first mounting portion 30 is only the mounting portion 30 b.Then, in a state in which the package L loaded on the first mountingportion 30 is unloaded, the delivery rotary-wing aircraft 1 departs fromthe destination and takes off. The delivery rotary-wing aircraft 1 movesto a departure place as a destination.

(Route B “from the Destination to the Departure Place”)

Route B is a flight route when the delivery rotary-wing aircraft 1 thathas separated (unloaded) the package L at the destination sets thedeparture place as a destination and returns to the departure place.

FIG. 9 is a model diagram showing a flight mode when the deliveryrotary-wing aircraft 1, from which the package has been separated, movesfrom the destination to the departure place. The operator operates acontrol device to raise the output of the power sections 14A to 14D ofthe rotary wing portions 10A to 10D, thereby increasing the numbers ofrotations of the rotary wings 12A to 12D. By the rotation of the rotarywings 12A to 12D, a lift necessary for lifting the delivery rotary-wingaircraft 1 is generated. When the lift exceeds the gravity by acting onthe delivery rotary-wing aircraft 1, the delivery rotary-wing aircraft 1leaves the ground and takes off the destination.

(A′) Aerial Stopping (Hovering)

The delivery rotary wing aircraft 1 flies on the same route as the routeA in the reverse direction and returns to the departure place.Basically, in route B, the flight mode of the delivery rotary-wingaircraft 1 is the same as that of the route A. In route B, since a loadis not loaded on the first mounting portion 30, the center of gravity Cgof the delivery rotary-wing aircraft 1 is moving vertically upward.Therefore, in order for the delivery rotary-wing aircraft 1 to fly routeB, an operator may set a new gain different from the gain used for routeA.

In route B, the delivery rotary-wing aircraft 1 rises and reaches acertain altitude. In route B, an altitude different from that of route Amay be set again. The delivery rotary-wing aircraft 1 that arrived atthe altitude performs aerial stopping (hovering).

(B′) Inclination of Arm Portion

In the arm portion 16 of the delivery rotary-wing aircraft 1 which isstopping in the air (hovering), the front rotary wing A is positionedlower than the rear rotary wing B so as to incline forwardly downward.Thereafter, the delivery rotary-wing aircraft 1 adjusts the numbers ofrotations of the rotary wings 12A to 12D after inclining the arm portion16 while hovering (aerial stopping).

(C′)-(E′) Adjustment of the Numbers of Rotations, Horizontal MovementPosture, Etc.

Next, in the delivery rotary-wing aircraft 1, the second supportingmember 26 and the first supporting member 24 are rotated leftward at 90°so that the second mounting portion 40 is the most distal end portionwith respect to the advancing direction, with the joint portion 28 as astarting point. The flight mode of the delivery rotary-wing aircraft 1is the horizontal movement posture in route B. The delivery rotary-wingaircraft 1 horizontally moves the distance from the sky above thedestination to the sky above the departure place while maintaining thehorizontal movement posture.

In the delivery rotary-wing aircraft 1 of the present invention, byinclining the arm portion 16, the forward bent posture that isdownwardly inclined with respect to the traveling direction ismaintained, and the numbers of rotations of the rotary wings 12A to 12Don which the arm portion 16 is mounted can be equalized. Whenhorizontally moving, the delivery rotary-wing aircraft 1 employs astructure in which the second mounting portion 40 is the most distal endportion with respect to the traveling direction, and the secondsupporting member 26 and the first supporting member 24 are linear. Thedelivery rotary-wing aircraft 1 can greatly reduce the air resistancewhen horizontally moving. Moreover, in route B, since the package L isnot loaded on the first mounting portion 30, the total weight of thedelivery rotary-wing aircraft 1 is reduced. Therefore, the horizontalmoving speed of the delivery rotary-wing aircraft 1 can be furtherimproved.

The delivery rotary-wing aircraft 1 moves horizontally and arrives abovethe departure place. In the departure place, in general, an updraft isnot generated but if some force due to the updraft or the like isapplied to the delivery rotary-wing aircraft 1, an operation of loweringthe center of gravity as described for route A may be performed.

Thus, the delivery rotary-wing aircraft 1 of the present invention can,even when the arm portion 16 has a certain angle around the connectionportion 22, make the rotational speeds of the rotary wings 12A to 12Dequal, thereby improving the moving speed of the delivery rotary-wingaircraft. In addition, a large amount of package can be loaded by thefirst mounting portion 30 of the delivery rotary-wing aircraft 1, makingit possible to cope with the payload.

Furthermore, even if the delivery rotary-wing aircraft 1 of the presentinvention receives an updraft by a high-rise building or the like, therotary-wing aircraft itself does not incline and can stably land on thedestination. Even after separating the package from the rotary-wingaircraft, the balance is not lost.

Second Embodiment

The delivery rotary-wing aircraft 1 of the second embodiment is of atype employing a ladder frame in the central portion 20 and the armportion 16 which are the basic structure of the rotary-wing aircraft.The delivery rotary-wing aircraft 1 of the second embodiment has a basicstructure of a ladder frame composed of four aluminum hollow squarebars. A space can be formed at the center of the ladder frame. The spacecan be changed according to the use of the rotary-wing aircraft, and alarge space can be formed. At the central portion of the ladder frame, asecond mounting part can be provided. Various attachments can beinstalled in the second mounting part. In the delivery rotary-wingaircraft 1 of the second embodiment, an attachment can be installed atthe central portion of the ladder frame according to its applications,it has an optimized frame shape, and thus, it can also be utilized as amulti-role rotary-wing aircraft.

Third Embodiment

In the third embodiment, a GPS antenna 42 for receiving a signal forpositioning is mounted on the distal end portion of the second mountingportion 40, and a joint portion 44 is provided so that the GPS antenna42 is always vertically upward. The joint portion 44 is provided on athird supporting member constituting the GPS antenna 42. Since thedelivery rotary-wing aircraft 1 can maintain the GPS antennahorizontally by a joint portion 44, so that it is possible to flywithout lowering the reception sensitivity.

That is, the reception sensitivity of the GPS antenna can be matchedbetween the ground surface and the sky. The delivery rotary-wingaircraft 1 of the third embodiment can also cope with multipath andjamming waves from the ground surface. Furthermore, the deliveryrotary-wing aircraft 1 of the third embodiment can improve a positioningaccuracy by adopting a choke ring antenna.

The delivery rotary-wing aircraft 1 of the third embodiment has a goodreception sensitivity of the GPS antenna even in areas where manyhigh-rise buildings are located and areas where radio wave disturbancesoccur frequently.

The delivery rotary-wing aircraft 1 of the third embodiment may beprovided with a parachute in the lower portion of the second mountingportion 40. Even when the delivery rotary-wing aircraft 1 cannot predictit, when the aircraft becomes uncontrollable by the operator, and whenthe battery runs short during flight, the rotary-wing aircraft will notfall. The delivery rotary-wing aircraft 1 can safely deliver the loadloaded on the first mounting portion 30 to the destination or the groundby opening the loaded parachute. The parachute is launched by operatingthe launcher mounted on the second mounting portion 40.

Although the embodiments of the present invention have been describedabove, the present invention is not limited to the above-describedembodiments, and all modifications of conditions and the like that donot depart from the gist are all within the scope of the presentinvention.

INDUSTRIAL APPLICABILITY

The delivery rotary-wing aircraft of the present invention can cope withthe updraft occurring in a high-rise building or the like. Therefore,the delivery rotary-wing aircraft of the present invention can expectthe use as a delivery rotary-wing aircraft dedicated for packagedelivery service, with tall buildings such as high-rise buildings aslanding grounds, and the use as a rotary-wing aircraft dedicated forindustrial package delivery in a warehouse or a factory. Further, thedelivery rotary-wing aircraft of the present invention can be used inaircraft related industries such as multicopters or drones, and furtherthe present invention can be preferably used not only as a rotary-wingaircraft for aerial photographing mounted with a camera or the like, butalso it can be used for various industries such as security field,agriculture, infrastructure monitoring and others.

EXPLANATION OF SIGN

-   -   1 delivery rotary-wing aircraft    -   10A to 10D rotary wing portion    -   12A to 12D rotary wing    -   14A to 14D power section    -   16A to 16D arm portion    -   20 central portion    -   22 connection portion (ball joint)    -   22 a socket    -   24 first supporting member (first mounting portion to connection        portion)    -   26 second supporting member (central portion to second mounting        portion)    -   242 adjustment mechanism    -   244 first supporting member (adjustment mechanism—joint portion)    -   26 second supporting member (central portion to second mounting        portion)    -   28 joint portion    -   30 first mounting part    -   L package (for delivery service)    -   30 a storage box    -   30 b mounting portion    -   40 second mounting part    -   42 GPS antenna

The invention claimed is:
 1. A delivery rotary-wing aircraft comprising:a plurality of rotary wings; a central portion to which a plurality ofarm portions for supporting the rotary wings are connected; a mountingportion for loading an object; a supporting member for connecting themounting portion with the central portion; and a connection portionequipped at between the central portion and the supporting member,wherein the plurality of arm portions are provided to extend from thecentral potion, wherein a center of lift occurring in the rotary-wingaircraft with rotations of the plurality of rotary wings and a center ofgravity of the rotary-wing aircraft coincide with a center of theconnection portion, and, wherein the supporting member is configured toextend downward.
 2. The delivery rotary-wing aircraft according to claim1, wherein the supporting member has a joint portion between theconnection portion and the mounting portion.
 3. The delivery rotary-wingaircraft according to claim 2, wherein, when the rotary-wing aircraftmoves in a horizontal direction, the rotary-wing aircraft rotates thesupporting member around the joint portion so that a posture of themounting portion keeps horizontal.
 4. The delivery rotary-wing aircraftaccording to claim 1, wherein the center of the connection portion ispositioned on a plane formed by the plurality of rotary wings.